摘要
微喷管内流体对壁面的粘性力和热传导可显著影响火箭发动机性能。通过出口亚声速层面积与出口面积比、推力和比冲损失等参数,评估了S-A和低Re数k-ε湍流模型、壁面初始温度和喷管构型因素对微喷管内粘性和热损失效应的影响。结果表明,两种湍流模型在计算粘性边界层上有一定的差异,粘性力造成推力损失22%;换热既减小粘性边界层尺寸,降低粘性作用,也降低微喷管比冲;升高微喷管壁面初始温度,能降低热量损失,增大其尺寸能减小粘性损失,二者均能提高比冲。
Characteristics of the rocket motor can be largely affected by viscous force and heat transfer of fluid to the wall of micro-nozzles. In this paper, the effects of turbulence models （S-A and low Re k-e models） , initial temperature and size of the micronozzle on viscous and heat loss were evaluated through parameters like the area ratio of subsonic layer to outlet, thrust and impulse loss et al. The results show that two turbulence models have some differences in calculating the subsonic layer; thrust losses attain 22% due to viscouse effects;heat transfer reduces not only the size of viscous boundary layer and the corresponding viscous effects, but also the impulse of micro-nozzle. Heat loss can be decreased through increasing initial temperature of the micro-nozzles wall, and viscous loss can be reduced by enlarging its size, thus improve impulse of the micro-nozzles.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2012年第1期57-63,共7页
Journal of Solid Rocket Technology
基金
总装备部预研基金资助项目
西北工业大学创业种子基金资助
